EP2982601B1 - Aircraft safety system - Google Patents

Aircraft safety system Download PDF

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Publication number
EP2982601B1
EP2982601B1 EP14717154.0A EP14717154A EP2982601B1 EP 2982601 B1 EP2982601 B1 EP 2982601B1 EP 14717154 A EP14717154 A EP 14717154A EP 2982601 B1 EP2982601 B1 EP 2982601B1
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EP
European Patent Office
Prior art keywords
aircraft
indicator
light
landing gear
sensor
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Active
Application number
EP14717154.0A
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German (de)
French (fr)
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EP2982601A1 (en
Inventor
Santiago RUANO RUEDA
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Individual
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Individual
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/26—Control or locking systems therefor
    • B64C25/28—Control or locking systems therefor with indicating or warning devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2203/00—Aircraft or airfield lights using LEDs

Definitions

  • the object of the present invention is an aircraft having an aircraft safety system which allows safely indicating the state of the aircraft through its own means, with respect to its availability to be able to move, i.e., if it is stopped with or without the parking brake or hand brake activated.
  • the safety system has, combined with field indicators, an aircraft safety system that allows indicating in a safe and reliable manner the state of the parking brake of the aircraft, and therefore acting accordingly without any danger whatsoever for maintenance and support crew, is achieved.
  • the present invention is comprised in the field of aircraft and the like, and it is particularly comprised in indicator systems.
  • the ground crew is unable to determine if the aircraft might perform an unexpected maneuver, or, in contrast, if it is in a completely stopped position through its own means without any intention of performing any maneuver.
  • Airbus A319, A320 and A321 aircraft have warning lights indicating the actuation of the actuation brake without having additional means increasing the safety of the indication of the state of the aircraft.
  • an object of the present invention is to develop an aircraft having an aircraft safety system which allows the ground crew tending to the aircraft to know when it is safe to approach the aircraft and perform the tasks they must perform, so a safety system such as the one described below and included in its essentiality in claim 1 has been developed.
  • An object of the present invention is an aircraft having an aircraft safety system for indicating when it is safe to approach an aircraft.
  • the aircraft safety system seeks to provide a visual indication to ground operators for the purpose of assuring safe and reliable information as to whether or not they can approach the aircraft.
  • the light indicators are arranged in the main landing gear and in the landing gear nose leg.
  • the system comprises a dual set of indicators.
  • the first indicator is a mechanical-type indicator which allows continuously displaying a surface of one color or another color, according to the state of the aircraft and particularly of the parking brake.
  • the second indicator is an electrically activated light indicator which is activated only when the conditions necessary for activation thereof are present, in addition to the aircraft being connected.
  • Both indicators are redundant regarding the same information, i.e., indicating the state of the aircraft, but the first indicator provides information about the state of the aircraft continuously, whereas the second indicator provides the information when the aircraft is energized.
  • the system comprises a control unit which provides activation signals to the indicators depending on input signals.
  • the control unit receives information from a sensor associated with the lever of the landing gear, from a microswitch or the like arranged on the landing gear itself which detects that the wheels are bearing weight.
  • the control unit When the information coming from the two indicated sensors is concurrent, the control unit considers that the landing gear has been deployed, that it is in contact with the ground. Depending on the signal from a sensor associated with the parking brake lever or the like plus the signal of hydraulic pressure sensor in the brake system of the aircraft, an indication will be given concerning the locking of the wheels by the action of the parking brake, at which time it sends an activation signal to the first indicator or mechanical indicator, which switches from one color to another, and another activation signal to the second indicator or light indicator which switches from one lighting color to another.
  • the color code adopted for indicating when it is safe to approach the aircraft can be any color code, as long as it is recognized and validated by the users.
  • the color green could indicate that it is not possible to approach the aircraft and the red to indicate that it is possible.
  • the power supply of the first type of indicator or mechanical indicator takes place from what is known in the sector as continuous power supply.
  • the power supply of the second type of indicator or light indicator takes place from what is known in the sector as power bus, which allows power supply when the battery power receptacle is energized. Furthermore, the light intensity of the LEDs that are part of the light indicator is regulated by a potentiometer depending on the "taxi light” of the aircraft, such that if the so-called “taxi light” is disconnected, the emitted light intensity will be lower, and in the opposite situation it will be higher.
  • Figure 1 shows the landing gear (3) of an aircraft where two types of indicators, a first type or mechanical indicator (1) and a second type or light indicator (2), are arranged on the outer side of the legs.
  • Figure 2 shows the landing gear leg (4) which has the two indicators (1) and (2) in the front part thereof.
  • Figure 3 shows the elements that are part of the safety system.
  • the first type of indicator or mechanical indicator (1) comprises a window which, depending on its position, shows either a first tab (1.1) or a second tab (1.2), of different colors, depending on the state of the aircraft.
  • This first indicator (1) is powered continuously from a continuous power supply (12) which assures constant power supply, so there will always be an indication of the state of the aircraft in relation to its state to allow the ground crew to approach or not.
  • the second type of indicator or light indicator (2) comprises first and second light means (2.1, 2.2), which can be LEDs or the like, of two different colors, and some or others will be activated according to the state of the aircraft to allow the ground crew to approach or not.
  • This second type of indicator (2) is powered from a power bus (13) through a potentiometer (14) controlling the brightness of the lighting means depending on the so-called “taxi light” (15) of the aircraft.
  • the activation of the lighting means is controlled by a control (5) receiving the information from:
  • control unit (5) sends a switching signal (9) to the first indicator (1) or mechanical indicator, making the window switch from one position or another, leaving the first tab (1.1) or the second tab (1.2) visible; and first and second activation signals (10, 11) for activating the first light means (2.1) or second light means (2.2), which turn the corresponding light means on or off.
  • the information about the first indicator (1) and about the second indicator (2) is consistent at all times.
  • test switch (16) which allows recognizing the state of the light signals of the light indicator (2) independently of the control (5).
  • Figure 4 shows the operating diagram of the two types of light indicators (1) and (2). Therefore, when the activation sensor of the landing gear (6) and the microswitch (7) is activated, it is verified whether or not the system is active. In the event that it is active, if the conditions for activating the parking brake (8), together with the activation of the hydraulic pressure sensor in brakes (17) are present, on one hand the first indicator or mechanical indicator (1), powered from the continuous power supply (12), is activated, leaving tab (1.1), for example, which is red, visible, whereas the second indicator or light indicator (2), powered from the power bus (13), would activate the light means (2.1) which would be of the same color as the previous one, i.e., red.
  • tab (1.2), which would be the color green, would be activated in the mechanical indicator (1), whereas the light means (2.2), which would be green, would be activated in the light indicator (2).
  • the red indication both in the first indicator or mechanical indicator (1) and in the second indicator or light indicator (2) appears only if the conditions necessary for it are present, otherwise green indications will appear.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Lighting Device Outwards From Vehicle And Optical Signal (AREA)
  • Audible And Visible Signals (AREA)

Description

    OBJECT OF THE INVENTION
  • As indicated in the title of the invention, the object of the present invention is an aircraft having an aircraft safety system which allows safely indicating the state of the aircraft through its own means, with respect to its availability to be able to move, i.e., if it is stopped with or without the parking brake or hand brake activated.
  • As a result of the control means that the safety system has, combined with field indicators, an aircraft safety system that allows indicating in a safe and reliable manner the state of the parking brake of the aircraft, and therefore acting accordingly without any danger whatsoever for maintenance and support crew, is achieved.
  • Therefore, the present invention is comprised in the field of aircraft and the like, and it is particularly comprised in indicator systems.
    • PRIOR ART
  • In the state of the art, once aircraft have landed they either head for the jet bridge or connecting point for the boarding or deboarding of passengers, or they remain stopped on a certain point of the runway.
  • During the time that the aircraft is idle, the ground crew is unable to determine if the aircraft might perform an unexpected maneuver, or, in contrast, if it is in a completely stopped position through its own means without any intention of performing any maneuver.
  • Sometimes the ground crew that tends to the aircraft approaches said aircraft in order to perform maintenance tasks without being fully certain of the complete immobilization of the aircraft through its own means, even situations of unexpected movement of the aircraft with the ground crew directly interacting with the aircraft being able to occur, with the subsequent danger for the crew and for the aircraft.
  • In the state of the art, Airbus A319, A320 and A321 aircraft have warning lights indicating the actuation of the actuation brake without having additional means increasing the safety of the indication of the state of the aircraft.
  • An aircraft having an aircraft safety system of this type is already known from the document US 20080033607 .
  • Therefore, an object of the present invention is to develop an aircraft having an aircraft safety system which allows the ground crew tending to the aircraft to know when it is safe to approach the aircraft and perform the tasks they must perform, so a safety system such as the one described below and included in its essentiality in claim 1 has been developed.
    • DESCRIPTION OF THE INVENTION
  • An object of the present invention is an aircraft having an aircraft safety system for indicating when it is safe to approach an aircraft.
  • The aircraft safety system seeks to provide a visual indication to ground operators for the purpose of assuring safe and reliable information as to whether or not they can approach the aircraft.
  • The light indicators are arranged in the main landing gear and in the landing gear nose leg.
  • The system comprises a dual set of indicators. The first indicator is a mechanical-type indicator which allows continuously displaying a surface of one color or another color, according to the state of the aircraft and particularly of the parking brake.
  • The second indicator is an electrically activated light indicator which is activated only when the conditions necessary for activation thereof are present, in addition to the aircraft being connected.
  • Both indicators are redundant regarding the same information, i.e., indicating the state of the aircraft, but the first indicator provides information about the state of the aircraft continuously, whereas the second indicator provides the information when the aircraft is energized.
  • The system comprises a control unit which provides activation signals to the indicators depending on input signals.
  • The control unit receives information from a sensor associated with the lever of the landing gear, from a microswitch or the like arranged on the landing gear itself which detects that the wheels are bearing weight.
  • When the information coming from the two indicated sensors is concurrent, the control unit considers that the landing gear has been deployed, that it is in contact with the ground. Depending on the signal from a sensor associated with the parking brake lever or the like plus the signal of hydraulic pressure sensor in the brake system of the aircraft, an indication will be given concerning the locking of the wheels by the action of the parking brake, at which time it sends an activation signal to the first indicator or mechanical indicator, which switches from one color to another, and another activation signal to the second indicator or light indicator which switches from one lighting color to another.
  • The color code adopted for indicating when it is safe to approach the aircraft can be any color code, as long as it is recognized and validated by the users. For example, the color green could indicate that it is not possible to approach the aircraft and the red to indicate that it is possible.
  • The power supply of the first type of indicator or mechanical indicator takes place from what is known in the sector as continuous power supply.
  • The power supply of the second type of indicator or light indicator takes place from what is known in the sector as power bus, which allows power supply when the battery power receptacle is energized. Furthermore, the light intensity of the LEDs that are part of the light indicator is regulated by a potentiometer depending on the "taxi light" of the aircraft, such that if the so-called "taxi light" is disconnected, the emitted light intensity will be lower, and in the opposite situation it will be higher.
  • Therefore as a result of the described aircraft safety system, redundant information about the state of the aircraft offering certainty to the ground crew tending to the aircraft as to whether or not it is safe to approach said aircraft is achieved.
    • DESCRIPTION OF THE DRAWINGS
  • To complement the description that is being made and for the purpose of aiding to better understand the features of the invention according to a preferred practical embodiment thereof, a set of drawings is attached as an integral part of said description in which the following has been depicted with an illustrative and nonlimiting character.
    • Figure 1 shows part of a landing gear where the two types of light indicators can be seen.
    • Figure 2 shows the aircraft nose leg which also has the types of light indicators.
    • Figure 3 shows the elements that are part of the aircraft safety system.
    • Figure 4 shows a flow chart of the operating conditions of the two types of light indicators.
    PREFERRED EMBODIMENT OF THE INVENTION
  • A preferred embodiment of the proposed invention is described below in view of the drawings.
  • Figure 1 shows the landing gear (3) of an aircraft where two types of indicators, a first type or mechanical indicator (1) and a second type or light indicator (2), are arranged on the outer side of the legs.
  • Figure 2 shows the landing gear leg (4) which has the two indicators (1) and (2) in the front part thereof.
  • Figure 3 shows the elements that are part of the safety system.
  • The first type of indicator or mechanical indicator (1) comprises a window which, depending on its position, shows either a first tab (1.1) or a second tab (1.2), of different colors, depending on the state of the aircraft.
  • This first indicator (1) is powered continuously from a continuous power supply (12) which assures constant power supply, so there will always be an indication of the state of the aircraft in relation to its state to allow the ground crew to approach or not.
  • The second type of indicator or light indicator (2) comprises first and second light means (2.1, 2.2), which can be LEDs or the like, of two different colors, and some or others will be activated according to the state of the aircraft to allow the ground crew to approach or not.
  • This second type of indicator (2) is powered from a power bus (13) through a potentiometer (14) controlling the brightness of the lighting means depending on the so-called "taxi light" (15) of the aircraft.
  • The activation of the lighting means is controlled by a control (5) receiving the information from:
    • a sensor (6) associated with the activation lever of the landing gear,
    • a microswitch (7) or the like associated with the wheels of the landing gear and indicating if the wheels are bearing weight,
    • a sensor associated with an actuation lever for actuating the parking brake (8),
    • a hydraulic pressure sensor (17) in the brake systems, which reads the hydraulic pressure in the brake systems.
  • Depending on the values of said sensors, the control unit (5) sends a switching signal (9) to the first indicator (1) or mechanical indicator, making the window switch from one position or another, leaving the first tab (1.1) or the second tab (1.2) visible; and first and second activation signals (10, 11) for activating the first light means (2.1) or second light means (2.2), which turn the corresponding light means on or off.
  • The information about the first indicator (1) and about the second indicator (2) is consistent at all times.
  • Furthermore, between the power bus (13) and the activation signals (10) and (11) for activating the light means (2.1) or (2.2) there is a test switch (16) which allows recognizing the state of the light signals of the light indicator (2) independently of the control (5).
  • Figure 4 shows the operating diagram of the two types of light indicators (1) and (2). Therefore, when the activation sensor of the landing gear (6) and the microswitch (7) is activated, it is verified whether or not the system is active. In the event that it is active, if the conditions for activating the parking brake (8), together with the activation of the hydraulic pressure sensor in brakes (17) are present, on one hand the first indicator or mechanical indicator (1), powered from the continuous power supply (12), is activated, leaving tab (1.1), for example, which is red, visible, whereas the second indicator or light indicator (2), powered from the power bus (13), would activate the light means (2.1) which would be of the same color as the previous one, i.e., red.
  • In the event that the system is not active, tab (1.2), which would be the color green, would be activated in the mechanical indicator (1), whereas the light means (2.2), which would be green, would be activated in the light indicator (2).
  • Therefore, the red indication both in the first indicator or mechanical indicator (1) and in the second indicator or light indicator (2) appears only if the conditions necessary for it are present, otherwise green indications will appear.

Claims (7)

  1. An aircraft comprising: landing gear, landing gear legs, an activation lever of the landing gear, a parking brake, an actuation lever for actuation the parking brake, brake systems, wheels and an aircraft safety system for indicating the state of the aircraft and for being able to safely approach said aircraft, whereby said aircraft system comprises:
    - two types of indicators, a first type or mechanical indicator (1), and a second type or light indicator (2), arranged on at least one of said landing gear legs,
    - a first sensor (6) associated with said activation lever of said landing gear,
    - a micro switch (7) or the like associated with said wheels of said landing gear and indicating if said wheels are bearing weight,
    - a second sensor (8) associated with said actuation lever for actuating said parking brake,
    - a hydraulic pressure sensor (17) in said brake systems,
    - a control unit (5) which receives information from said first sensors (6), said second sensor (8), said hydraulic pressure sensor (17) and said micro switch (7) wherein
    said light indicator (2) comprises first light means (2.1) and second light means (2.2) of a different colour to that of said first light means (2.1) and
    said control unit (5) sends a switching signal (9) to said first indicator (1) or mechanical indicator, and a first activation signal (10) for activating said first light means (2.1) or a second activation signal (11) for activating said second light means (2.2), depending on the values of said first sensor (6), said second sensor (8) and said hydraulic pressure sensor (17).
  2. The aircraft according to claim 1, characterized in that the first type of indicator or mechanical indicator (1) comprises a window which, depending on its position, shows either a first tab (1.1) or a second tab (1.2), of different colors, depending on the state of the aircraft.
  3. The aircraft according to claim 2, characterized in that the first indicator (1) is powered continuously from a continuous power supply (12).
  4. The aircraft according to claim 1, characterized in that the second type of indicator or light indicator (2) comprises said first and second light means (2.1, 2.2) and some or others will be activated according to the state of the aircraft.
  5. The aircraft according to claim 4, characterized in that the second type of indicator (2) is powered from a power bus (13) of the aircraft.
  6. The aircraft according to claim 5, characterized in that the power is supplied from said power bus (13) through a potentiometer (14) controlling the brightness of said light means depending on a light (15) of the aircraft.
  7. The aircraft according to claim 5, characterized in that between said power bus (13) and said first and second activation signals (10, 11) for activating said first and second light means (2.1, 2.2) there is a test switch (16) which allows recognizing independently of the control (5) the state of the light signals of the light indicator (2).
EP14717154.0A 2013-04-04 2014-04-01 Aircraft safety system Active EP2982601B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ES201330486A ES2504915B2 (en) 2013-04-04 2013-04-04 Aircraft Security System
PCT/ES2014/070248 WO2014162032A1 (en) 2013-04-04 2014-04-01 Aircraft safety system

Publications (2)

Publication Number Publication Date
EP2982601A1 EP2982601A1 (en) 2016-02-10
EP2982601B1 true EP2982601B1 (en) 2020-04-29

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Application Number Title Priority Date Filing Date
EP14717154.0A Active EP2982601B1 (en) 2013-04-04 2014-04-01 Aircraft safety system

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EP (1) EP2982601B1 (en)
ES (1) ES2504915B2 (en)
WO (1) WO2014162032A1 (en)

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US9802716B2 (en) * 2015-06-06 2017-10-31 Borealis Technical Limited Aircraft landing gear drive wheel identification system
US9975627B2 (en) * 2016-10-18 2018-05-22 Goodrich Corporation Systems and methods for aircraft parking brakes with multiple control locations
US10272888B2 (en) 2016-12-09 2019-04-30 Goodrich Corporation Systems and methods for aircraft emergency and park brakes
EP3336485B1 (en) 2016-12-15 2020-09-23 Safran Landing Systems UK Limited Aircraft assembly including deflection sensor
GB2563948A (en) 2017-06-30 2019-01-02 Airbus Operations Ltd Aircraft landing gear assembly
GB2563949A (en) * 2017-06-30 2019-01-02 Airbus Operations Ltd Aircraft landing gear assembly
GB2563945A (en) * 2017-06-30 2019-01-02 Airbus Operations Ltd Aircraft landing gear assembly

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US20090210105A1 (en) * 2006-05-15 2009-08-20 Lusby Brock D Air-ground detection system and method
US20080033607A1 (en) * 2006-06-01 2008-02-07 Bob Zeliff Monitoring system for aircraft landing system
US20090014261A1 (en) * 2006-08-29 2009-01-15 Jonathan Sidney Edelson Apparatus for controlling aircraft parking brakes
GB2450796A (en) * 2007-07-05 2009-01-07 Borealis Tech Ltd Remote control of an aircraft parking brakes and/or APU
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Also Published As

Publication number Publication date
ES2504915A1 (en) 2014-10-08
EP2982601A1 (en) 2016-02-10
WO2014162032A1 (en) 2014-10-09
ES2504915B2 (en) 2015-03-24

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